14 CFR Part 39 AD 55-26-01 Airworthiness Directives; DOUGLAS A-26 Aircraft PDF Copy (If Available): AGENCY: Federal Aviation Administration, DOT Regulatory Information 55-26-01 DOUGLAS: Applies to A-26 Aircraft Having Rear Fuselage Fuel Tank Installation. To be accomplished prior to actuation of fuselage fuel tank. Because of an explosion in the air and loss of aircraft, instructions were issued October 12, 1955, to deactivate the rear fuselage fuel tank on the above aircraft until further notice. If the following modification, or its equivalent, is accomplished this fuel tank may be reactivated: 1. Provide fume tight closure and sealing of bulkheads at Stations 332 and 369. This should include tight fitting grommets or fairleads around control cables, or other members passing through bulkhead. 2. Remove all electrical equipment and oxygen tanks, if installed, from the tank compartment. Relocate elsewhere in the airplane as required. 3. Provide insulation around any electrical terminals in tank bay. 4. Provide adequate ventilation airscoop on top or side of tank compartment and exit vent on bottom. Provide drain holes in bottom of compartment to assure complete fuel drainage. 5. Ascertain that fuel tank, filler, cap, scupper, drain, and attaching lines and fittings are airworthy.

	14 CFR Part 39 AD 61-11-05 Airworthiness Directives; DOUGLAS All Models A-26 (B-26) Series Aircraft PDF Copy (If Available): Preamble Information AGENCY: Federal Aviation Administration, DOT DATES: Effective June 29, 1961. Regulatory Information 61-11-05 DOUGLAS: Amdt. 291 Part 507 Federal Register May 30, 1961. Applies to All Models A-26 (B-26) Series Aircraft. Compliance required as indicated. As a result of several reported cases of severe corrosion of the wing structure in the area beneath the wing fuel tanks, the following must be accomplished at the next periodic inspection and every periodic inspection thereafter, until (b) is accomplished: (a) Remove the center wing fuel tanks and inspect the internal wing structure for corrosion. If corrosion is found, FAA approved repairs and/or replacement of affected parts must be made prior to further flight. Also, inspect the sponge rubber mats under the fuel cells, and if found deteriorated they must be replaced prior to next flight. (b) When the sponge rubber mats have been replaced with closed cell neoprene sponge mats, or equivalent, and any corrosion damage present is repaired, the special inspection of (a) is no longer required. This directive effective June 29, 1961.

	14 CFR Part 39 Amendment 39-5031; AD 84-15-02 Airworthiness Directives; DOUGLAS A-26/B26 Series Airplanes PDF Copy (If Available): Preamble Information AGENCY: Federal Aviation Administration, DOT DATES: Effective April 16, 1985. Regulatory Information 84-15-02 DOUGLAS AIRCRAFT COMPANY: Amendment 39-5031. Applies to Douglas Aircraft Model A-26/B26 series airplanes certificated in all categories. Compliance schedule as prescribed in the body of the AD, unless previously accomplished. To prevent loss of wing structural integrity due to failure of a lower spar cap, accomplish the following: A. Within ten (10) hours time in service after the effective date of this AD, perform a visual dye penetrant inspection of the lower forward and aft spar cap, outboard and inboard of each nacelle in the area where the nacelle fairing upper edge runs across the lower spar cap surface. Trim the fairing edge if necessary, to ensure that the fairing edge is smooth and that there is a minimum of one-sixteenth inch (1/16") clearance between the fairing and spar cap surface. B. If no cracking or fretting of the spar cap is detected, repeat the inspection for cracks, surface clearance, and condition in accordance with Paragraph A. of this AD at intervals not to exceed 500 hours time in service. C. If any evidence of cracking or fretting is found in the spar caps, polish out to a machine finish not to exceed approximately 125 microinches on both sides of the damaged area to a maximum depth of 0.030 inches and repeat the inspection of Paragraph A., above. Continue to inspect in accordance with Paragraph A. at intervals not to exceed 30 hours time in service. D. If cracking or fretting in excess of 0.030 inches in a spar cap is detected, repair in a manner approved by the Manager, Western Aircraft Certification Office, FAA, Northwest Mountain Region, Hawthorne, California. E. For those aircraft which have been modified to incorporate a steel or titanium lower front spar cap strap (in the area where the nacelle fairing upper edge is in contact with the lower wing surface) in accordance with AD 64-12-03, the requirements of Paragraph A. of this AD are applicable only to the lower aft spar cap, outboard and inboard of each nacelle. F. Within 72 hours after performing the inspections required by Paragraph A., above, report the results of the inspections to the Manager, Western Aircraft Certification Office, ANM-170W, FAA, Northwest Mountain Region, 15000 Aviation Blvd., Hawthorne, California. Mailing address: P.O. Box 92007, Worldway Postal Center, Los Angeles, California 90009. The reports should cite the airplane registration and serial number, crack location and extent of damage, total airplane operating hours, and time since last inspection. G. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections required by this AD. H. Alternate inspections, modifications, or other actions which provide an acceptable level of safety may be used when approved by the Manager, Western Aircraft Certification Office, FAA, Northwest Mountain Region, Hawthorne, California. This amendment becomes effective April 16, 1985, and it was effective earlier to all recipients of priority mail AD 84-15-02, issued August 1, 1984.

	14 CFR Part 39 AD 56-18-03 Airworthiness Directives; DOUGLAS All Models A-26B and A-26C Aircraft PDF Copy (If Available): Preamble Information AGENCY: Federal Aviation Administration, DOT Regulatory Information 56-18-03 DOUGLAS: Applies to All Models A-26B and A-26C Aircraft. Compliance required prior to September 5, 1956, and each periodic inspection thereafter. Numerous cases have been discovered of cracks in the nose gear cross beam assembly of certificated A-26 aircraft, developing at the inboard end of the trunnion journal. Accordingly, to reduce the possibility of failure of the wheel cross beam assemblies, the following inspection is required. (a) Remove the nose wheel cross beam assembly, P/N 5280335, or 5280336, or 5123942 or 5123943. (b) Using magnetic particle, dye penetrant or x-ray inspection equipment, inspect the 5-inch outboard portion of the beam and trunnion assembly for cracks, measuring from the trunnion journal inboard and paying particular attention to the area around the trunnion's shoulder and inboard of the welded area of the strap. (c) Cross beam assemblies found cracked during this inspection must be replaced. (USAF Technical Order 1B-26-519, dated April 9, 1956, covers this same subject.)

	14 CFR Part 39 Amendment 39-6271; AD 81-13-06 R2 HAMILTON STANDARD: Hydromatic (noncounterweighted) propellers with aluminum blades PDF Copy (If Available): Preamble Information AGENCY: Federal Aviation Administration, DOT DATES: Effective September 15, 1989. Regulatory Information 81-13-06 R2 HAMILTON STANDARD: Amendment 39-4133 as revised by Amendment 39- 4409 is further revised by Amendment 39-6271. Applicability: Hamilton Standard Hydromatic (noncounterweighted) propellers with aluminum blades that use engine oil for pitch control (does not apply to propellers with integral oil control or to propellers with steel blades) of the following types: 22D30, 22D40, 23D40, 23E50, 23E60, 24D50, 24E60, 33D50, 33E60, 34D50, 34D51, 34E60, 43D50, 43D51, 43E60, and 43H60, as installed on various reciprocating engine powered aircraft such as, but not limited to: Beech D17 and D18, Boeing 377 series, Canadair Model 4 and CL-215, Curtiss-Wright C-46, DeHavilland DHC-2, DHC-3, and DHC-4, General Dynamics (Convair) T-29, 240, 340, and 440 series, Gulfstream American (Grumman) G-12A, G164, F4U, S-2F, TBM, and W-2F series, Lockheed L-10, L-12, 049, 749, 1049, 1649 series, Martin 202 and 404 series, McDonnell Douglas B-26, DC-3, DC-4, DC-6, and DC-7 series, North American AT-6, B-25, P-51, SNJ-5, T-6 and T-28. Compliance: Required as indicated, unless already accomplished. To prevent propeller blade failure due to corrosion and fatigue, accomplish the following: (a) Inspect propeller blades within the next 90 days after July 1, 1982, or within 18 months since last inspection, whichever occurs later, for corrosion in the blade fillet and shank area, particularly under the teflon friction reduction strip and the resin corrosion barrier, in accordance with Hamilton Standard Aluminum Blade Overhaul Manual No. 130B, dated March 1, 1980, previously incorporated by reference on June 28, 1982, in AD 81-13-06. Thereafter, if corrosion is found reinspect at intervals not to exceed 18 months since the last inspection. (b) For propellers with all installed blades having no corrosion at the last inspection, the 18 month reinspection interval may be increased as follows: (1) Reinspect between 33 and 39 months since the last inspection. If corrosion is found to be beyond repairable limits return to the 18 month reinspection interval required by paragraph (a). If corrosion is found to be within repairable limits the reinspection interval cannot exceed a 36 month reinspection schedule. (2) If no corrosion is found at the last 33 to 39 month reinspection in accordance with paragraph (b)(1), then thereafter reinspect at intervals not to exceed 60 months. If corrosion is found to be beyond repairable limits at any reinspection interval return to the 18 month reinspection interval required by paragraph (a). If corrosion is found to be within repairable limits the reinspection interval may remain on a schedule not to exceed 60 months. (c) Prior to further flight, blades with corrosion in the fillet or shank area must be replaced with an airworthy blade or repaired in accordance with Hamilton Standard Aluminum Blade Overhaul Manual No. 130B, dated March 1, 1980. (d) Disassembled propeller blades preserved in accordance with Hamilton Standard Aluminum Blade Overhaul Manual No. 130B, dated March 1, 1980, need not include storage time when computing the time since last inspection. (e) Upon submission of substantiating data by an owner or operator through an FAA Airworthiness Inspector, the Manager, Boston Aircraft Certification Office, Engine and Propeller Directorate, Aircraft Certification Service, Federal Aviation Administration, 12 New England Executive Park, Burlington, Massachusetts 01803, may adjust the compliance times specified in this AD or approve an equivalent means of compliance with this AD. NOTE: Extensions to the compliance schedule previously granted to owners/operators are still applicable to this amendment. These extensions which are beyond a 39 month reinspection interval may be extended to 60 months as provided in paragraph (b)(2). (f) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of the inspection required by this AD. This AD revises AD 81-13-06 R1, Amendment 39-4409, (47 FR 36217; August 19, 1982), which revised AD 81-13-06, Amendment 39-4133. This amendment (39-6271, AD 81-13-06 R2) becomes effective on September 15, 1989

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